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US10851815B2 - Hydraulic circuit for operating an aircraft landing gear - Google Patents

Hydraulic circuit for operating an aircraft landing gear Download PDF

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Publication number
US10851815B2
US10851815B2 US16/691,065 US201916691065A US10851815B2 US 10851815 B2 US10851815 B2 US 10851815B2 US 201916691065 A US201916691065 A US 201916691065A US 10851815 B2 US10851815 B2 US 10851815B2
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Prior art keywords
depressurization
valve
operating
hydraulic circuit
distributors
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US16/691,065
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US20200164970A1 (en
Inventor
David Frank
Jean-Luc Belleval
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Safran Landing Systems SAS
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Safran Landing Systems SAS
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Publication of US20200164970A1 publication Critical patent/US20200164970A1/en
Assigned to SAFRAN LANDING SYSTEMS reassignment SAFRAN LANDING SYSTEMS ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FRANK, DAVID
Assigned to SAFRAN LANDING SYSTEMS reassignment SAFRAN LANDING SYSTEMS ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BELLEVAL, JEAN-LUC
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B20/00—Safety arrangements for fluid actuator systems; Applications of safety devices in fluid actuator systems; Emergency measures for fluid actuator systems
    • F15B20/004—Fluid pressure supply failure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18—Operating mechanisms
    • B64C25/22—Operating mechanisms fluid
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18—Operating mechanisms
    • B64C25/26—Control or locking systems therefor
    • B64C25/30—Control or locking systems therefor emergency actuated
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18—Operating mechanisms
    • B64C25/26—Control or locking systems therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B13/00—Details of servomotor systems ; Valves for servomotor systems
    • F15B13/02—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors
    • F15B13/06—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with two or more servomotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/30—Directional control
    • F15B2211/305—Directional control characterised by the type of valves
    • F15B2211/3056—Assemblies of multiple valves
    • F15B2211/3059—Assemblies of multiple valves having multiple valves for multiple output members
    • F15B2211/30595—Assemblies of multiple valves having multiple valves for multiple output members with additional valves between the groups of valves for multiple output members

Definitions

  • Aircrafts equipped with retractable landing gears that can be moved between a retracted position and an extended position using various operating actuators are known.
  • the landing gear is stabilized in the retracted position by means of hydraulically operated latching boxes. The same applies to the doors that close the cargo bays in which the landing gear is retracted.
  • the hydraulic circuit first comprises a general valve 1 comprising a supply position in which a supply line LA of the circuit is pressurized to supply pressure, and a return position in which the supply line LA returns.
  • the return position is a stable rest position here, and the supply position is selected using an electric control.
  • the circuit consists of two main lines, including a pressure line LP to supply pressure to the distributors supplying the hydraulic components of the circuit, and a return line LR connected to the aircraft return.
  • the circuit includes a depressurization valve 2 located here downstream of the general valve 1 and which, in an open position, connects the pressure line LP to the supply line LA and the return line LR to return, and, in a depressurization position, connects the pressure line LP and the return line LR to return.
  • the open position is a stable rest position.
  • the pressure LP and return LR lines lead here to a first 4-way, three-position distributor connected to an operating cylinder 3 adapted to rotate an undercarriage 10 about an axis 11 , between a retracted position shown here and an extended position.
  • the valve 4 selectively connects an extension line leading here to a plenum chamber 3 A of the actuating cylinder 3 and a retraction line leading to an annular chamber 3 B of the operating cylinder 3 with the pressure LP and return LR lines.
  • the pressure LP and return LR lines also lead to a second two-position distributor 6 connected to a latching box 5 single-acting release actuator (the actuator is integrated into the latching box here).
  • the hook of the latching box 5 is adapted to close automatically on a finger of the undercarriage 10 when it reaches the retracted position to maintain it in that position. It is therefore necessary to release the hook to allow the undercarriage 10 to move to the extended position.
  • the hydraulic circuit will also include a valve to supply a door actuating cylinder, and a distributor to release a hook maintaining the doors in the closed position.
  • the pressure LP and return LR lines then terminate at said distributors as they terminate at the distributors 4 and 6 . All this equipment is of course replicated for each of the undercarriages of the landing gears, although they are not represented here.
  • the retraction chamber of the operating cylinder(s) (in this case the chamber 3 B) should be positioned to return.
  • a mechanical emergency control in the form of a lever 12 operated by the aircraft pilot, which on the one hand forces the release of the hooks of the latching boxes 5 using a cable connection 13 , and on the other hand forces the depressurization valve 2 to move into the depressurization position, which allows any fluid contained in the actuating cylinder 3 to flow if necessary to the aircraft sump, and in particular the fluid contained in the retraction chamber 3 B, without any significant resistance, when the undercarriage is lowered to the extended position, regardless of the position of the distributor 4 .
  • the invention aims to provide a simplified hydraulic circuit to allow the landing gear(s) to be extended in the event of a loss of pressure.
  • the depressurization valve is returned in a stable manner to the depressurization position, and is moved into the open position only in response to the presence of supply pressure downstream of the general valve.
  • the depressurization valve is by default in the depressurization state. It can only be moved to the open position if the general valve has admitted supply pressure into the circuit. Therefore, the general valve must be in the supply position and supply pressure must be present upstream of the general valve for the depressurization valve to be in the open position. If the general valve fails, or the aircraft pumps are no longer driven, then the depressurization valve automatically moves into the depressurization position without any action by the pilot, which greatly simplifies the hydraulic circuit by eliminating any mechanical or motorized control of the depressurization valve. In addition, the depressurization valve is activated each time the undercarriages are operated, so that their operation can easily be monitored.
  • FIG. 1 the already detailed FIG. 1 showing the prior art:
  • FIG. 2 is a schematic view of a hydraulic circuit for operating an aircraft landing gear according to a first particular embodiment of the invention
  • FIG. 3 is a schematic view of a hydraulic circuit for operating an aircraft landing gear according to a second particular embodiment of the invention.
  • the circuit illustrated here is very similar to that in FIG. 1 , and the common elements have common references.
  • the reader should refer to their description in the introductory part hereof.
  • the main difference with the circuit of the prior art is in the depressurization valve 102 , whose stable position imposed by the return spring 105 is now the depressurization position.
  • the open position is controlled here by means of a hydraulic control 103 which is only able to overcome the force of the return spring 105 if supply pressure has been admitted into the supply line LA, i. e. if the general valve 1 has been controlled to the supply position AND if supply pressure has been supplied to the circuit by the aircraft pumps or an accumulator.
  • a bypass 104 is provided from a branch of the supply line LA to supply the hydraulic control 103 .
  • the depressurization valve 102 is no longer mechanically operated by the lever 12 .
  • the depressurization valve 102 operates fully automatically, with the hydraulic circuit being depressurized by default except in the specific phases of undercarriages operation.
  • the depressurization valve 102 which allows any fluid contained in the operating cylinder 3 to flow if necessary to the aircraft sump, and in particular the fluid contained in the retraction chamber 3 B, without any significant resistance, when the undercarriage is lowered to the extended position, regardless of the position of the distributor 4 .
  • the depressurization valve 202 is now arranged on a line of the circuit from the distributor 6 to the retraction chamber 3 B of the actuating cylinder 3 .
  • the stable position of the depressurization valve 202 is now the depressurization position.
  • the open position is controlled here by means of a hydraulic control 203 which is only able to overcome the force of the return spring 205 if supply pressure has been admitted into the supply line LA, i. e. if the general valve 1 has been controlled to the supply position AND if supply pressure has been supplied to the circuit by the aircraft pumps or an accumulator.
  • a bypass 204 is provided from a branch of the supply line LA to supply the hydraulic control 203 .
  • the depressurization valve 202 is no longer mechanically operated by the lever 12 .
  • the depressurization valve 102 operates fully automatically, with the hydraulic circuit being depressurized by default except in the specific phases of undercarriages operation.
  • the depressurization valve 202 allows any fluid contained in the retraction chamber 3 B to flow if necessary to the aircraft sump without significant resistance when the landing gear is lowered to the extended position, regardless of the position of the distributor 4 .
  • the hydraulic circuit shall also include a distributor to supply a door actuating cylinder, and a distributor to release a hook maintaining the doors in the closed position.
  • the pressure LP and return LR lines then terminate at said distributors as they terminate at the distributors 4 and 6 . All this equipment is of course replicated for each of the undercarriages of the landing gears, although they are not represented here.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Fluid-Pressure Circuits (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Mechanically-Actuated Valves (AREA)
  • Fluid-Driven Valves (AREA)
US16/691,065 2018-11-23 2019-11-21 Hydraulic circuit for operating an aircraft landing gear Active US10851815B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1871798 2018-11-23
FR1871798A FR3088898B1 (fr) 2018-11-23 2018-11-23 Circuit hydraulique de manœuvre de train d’atterrissage d’aéronef

Publications (2)

Publication Number Publication Date
US20200164970A1 US20200164970A1 (en) 2020-05-28
US10851815B2 true US10851815B2 (en) 2020-12-01

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ID=66049256

Family Applications (1)

Application Number Title Priority Date Filing Date
US16/691,065 Active US10851815B2 (en) 2018-11-23 2019-11-21 Hydraulic circuit for operating an aircraft landing gear

Country Status (6)

Country Link
US (1) US10851815B2 (fr)
EP (1) EP3656665B1 (fr)
CN (1) CN111216879B (fr)
CA (1) CA3062434C (fr)
ES (1) ES2881655T3 (fr)
FR (1) FR3088898B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20240317390A1 (en) * 2023-03-21 2024-09-26 Goodrich Corporation Hydraulic motor start assist

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112173085B (zh) * 2020-09-25 2023-03-28 中国直升机设计研究所 一种直升机起落架收放液压控制系统及方法
CN114408161B (zh) * 2021-12-28 2023-05-30 中国航空工业集团公司金城南京机电液压工程研究中心 一种三余度双腔作动器
CN117184442B (zh) * 2023-10-09 2025-07-15 中国飞机强度研究所 一种飞机起落架疲劳试验控制系统及其方法

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080087766A1 (en) 2006-10-17 2008-04-17 Messier-Bugatti Architecture for a hydraulic system for operating aircraft landing gear
US20090050736A1 (en) * 2005-08-04 2009-02-26 Messier-Dowty Limited Landing gear
EP2070818A1 (fr) 2007-12-13 2009-06-17 Messier-Bugatti Procédé d'alimentation en énergie d'actionneurs associés à un train d'atterrissage d'aéronef
GB2469484A (en) 2009-04-15 2010-10-20 Ge Aviat Systems Ltd Aircraft landing gear hydraulic actuation system
US8028954B2 (en) * 2006-10-17 2011-10-04 Messier-Bugatti Architecture for a hydraulic system for operating aircraft landing gear
US8807480B2 (en) * 2011-11-09 2014-08-19 Messier-Bugatti-Dowty Method of extending aircraft undercarriages in emergency mode
US9422052B2 (en) * 2012-12-04 2016-08-23 Sumitomo Precision Products Co., Ltd. Electro hydrostatic actuator system for retracting/extending landing gear
US10106248B2 (en) * 2013-06-14 2018-10-23 Bombardier Inc. Apparatus and method for controlling landing gear
US20200148339A1 (en) * 2018-11-14 2020-05-14 Safran Landing Systems Method for securing an aircraft wheel drive actuator in an open position

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Publication number Priority date Publication date Assignee Title
GB9923620D0 (en) * 1999-10-07 1999-12-08 Normalair Garrett Ltd Hydraulic system for aircraft landing gear
FR2898866B1 (fr) * 2006-03-22 2008-11-21 Airbus France Sas Distributeur hydraulique pour train d'atterrissage d'avion
US7815143B2 (en) * 2006-08-11 2010-10-19 The Boeing Company Aircraft landing gear truck orientation for noise reduction
GB2483472B (en) * 2010-09-08 2012-08-15 Messier Dowty Ltd Aircraft landing gear
KR20130067194A (ko) * 2011-12-13 2013-06-21 김광섭 파이어 알람
US9823670B2 (en) * 2014-11-25 2017-11-21 The Boeing Company Engine driven pump (EDP) automatic depressurization system

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090050736A1 (en) * 2005-08-04 2009-02-26 Messier-Dowty Limited Landing gear
US8028954B2 (en) * 2006-10-17 2011-10-04 Messier-Bugatti Architecture for a hydraulic system for operating aircraft landing gear
EP1914164A1 (fr) 2006-10-17 2008-04-23 Messier-Bugatti Architecture de système hydraulique de manoeuvre des atterrisseurs d'un aéronef
US20080087766A1 (en) 2006-10-17 2008-04-17 Messier-Bugatti Architecture for a hydraulic system for operating aircraft landing gear
US8136760B2 (en) * 2006-10-17 2012-03-20 Messier-Bugatti-Dowty Architecture for a hydraulic system for operating aircraft landing gear
EP2070818A1 (fr) 2007-12-13 2009-06-17 Messier-Bugatti Procédé d'alimentation en énergie d'actionneurs associés à un train d'atterrissage d'aéronef
US20090152394A1 (en) 2007-12-13 2009-06-18 Messier-Bugatti Method of feeding energy to actuators associated with an aircraft undercarriage
US8393565B2 (en) * 2007-12-13 2013-03-12 Messier-Bugatti-Dowty Method of feeding energy to actuators associated with an aircraft undercarriage
GB2469484A (en) 2009-04-15 2010-10-20 Ge Aviat Systems Ltd Aircraft landing gear hydraulic actuation system
US8418958B2 (en) * 2009-04-15 2013-04-16 Ge Aviation Systems Limited Landing gear actuation control system
US8807480B2 (en) * 2011-11-09 2014-08-19 Messier-Bugatti-Dowty Method of extending aircraft undercarriages in emergency mode
US9422052B2 (en) * 2012-12-04 2016-08-23 Sumitomo Precision Products Co., Ltd. Electro hydrostatic actuator system for retracting/extending landing gear
US10106248B2 (en) * 2013-06-14 2018-10-23 Bombardier Inc. Apparatus and method for controlling landing gear
US20200148339A1 (en) * 2018-11-14 2020-05-14 Safran Landing Systems Method for securing an aircraft wheel drive actuator in an open position

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
French Search Report for 1871798 dated Jun. 3, 2019.

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20240317390A1 (en) * 2023-03-21 2024-09-26 Goodrich Corporation Hydraulic motor start assist

Also Published As

Publication number Publication date
ES2881655T3 (es) 2021-11-30
CA3062434A1 (fr) 2020-05-23
EP3656665B1 (fr) 2021-06-02
FR3088898A1 (fr) 2020-05-29
CN111216879A (zh) 2020-06-02
CA3062434C (fr) 2021-07-20
US20200164970A1 (en) 2020-05-28
EP3656665A1 (fr) 2020-05-27
FR3088898B1 (fr) 2020-12-18
CN111216879B (zh) 2023-06-13

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